NASA Supercritical Airfoils PDF Download
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Author: Charles D. Harris
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 80
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Book Description
Author: Charles D. Harris
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 80
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Book Description
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 344
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Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722660826
Category :
Languages : en
Pages : 76
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Book Description
The NASA supercritical airfoil development program is summarized in a chronological fashion. Some of the airfoil design guidelines are discussed, and coordinates of a matrix of family related supercritical airfoils ranging from thicknesses of 2 to 18 percent and over a design lift coefficient range from 0 to 1.0 are presented. Harris, Charles D. Langley Research Center...
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 128
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Book Description
Author: Renaldo V. Jenkins
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 64
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Three high lift systems for a 9.3 percent blunt based, supercritical airfoil were designed, fabricated, and wind tunnel tested. A method for calculating the viscous flow about two dimensional multicomponent airfoils was evaluated by comparing its predictions with test data. A comparison of high lift systems derived from supercritical airfoils with high lift systems derived from conventional airfoils is presented. The high lift systems for the supercritical airfoil were designed to achieve maximum lift and consisted of: (1) a single slotted flap, (2) a double slotted flap and a leading edge slat, and (3) a triple slotted flap and a leading edge slat. Aerodynamic force and moment data and surface pressure data are presented for all configurations and boundary layer and wake profiles for the single slotted flap configuration. The wind-tunnel models, test facilities and instrumentation, and data reduction are described.
Author: E. Omar
Publisher:
ISBN:
Category :
Languages : en
Pages : 100
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Book Description
Author: National Aeronautics and Space Adm Nasa
Publisher:
ISBN: 9781731325259
Category :
Languages : en
Pages : 122
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Book Description
The effects of Mach number and Reynolds number on the experimental surface pressure distributions and transition patterns for a large chord, swept supercritical airfoil incorporating an active Laminar Flow Control suction system with spanwise slots are presented. The experiment was conducted in the Langley 8 foot Transonic Pressure Tunnel. Also included is a discussion of the influence of model/tunnel liner interactions on the airfoil pressure distribution. Mach number was varied from 0.40 to 0.82 at two chord Reynolds numbers, 10 and 20 x 1,000,000, and Reynolds number was varied from 10 to 20 x 1,000,000 at the design Mach number. Harris, Charles D. and Brooks, Cuyler W., Jr. and Clukey, Patricia G. and Stack, John P. Langley Research Center BOUNDARY LAYER CONTROL; LAMINAR FLOW; SUPERCRITICAL AIRFOILS; SWEPT WINGS; TRANSONIC FLOW; WING SLOTS; COMPUTATIONAL FLUID DYNAMICS; INTERACTIONAL AERODYNAMICS; MACH NUMBER; PRESSURE DISTRIBUTION; REYNOLDS NUMBER; SUCTION; WIND TUNNEL TESTS...
Author: E. Omar
Publisher:
ISBN:
Category :
Languages : en
Pages : 232
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Book Description
Three high lift systems for a 9.3 percent blunt based, supercritical airfoil were designed, fabricated, and wind tunnel tested. A method for calculating the viscous flow about two dimensional multicomponent airfoils was evaluated by comparing its predictions with test data. A comparison of high lift systems derived from supercritical airfoils with high lift systems derived from conventional airfoils is presented. The high lift systems for the supercritical airfoil were designed to achieve maximum lift and consisted of: (1) a single slotted flap, (2) a double slotted flap and a leading edge slat, and (3) a triple slotted flap and a leading edge slat. Aerodynamic force and moment data and surface pressure data are presented for all configurations and boundary layer and wake profiles for the single slotted flap configuration. The wind-tunnel models, test facilities and instrumentation, and data reduction are described.
Author: Charles D. Harris
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
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Book Description
